用Monte Carlo法分析固体火箭发动机推力终止过程内弹道散布

推进技术 ›› 1997, Vol. 18 ›› Issue (6): 31-35.

用Monte Carlo法分析固体火箭发动机推力终止过程内弹道散布

杨涛,郑荣跃,方丁酉,夏智勋

国防科技大学航天技术系!长沙;410073;国防科技大学航天技术系!长沙;410073;国防科技大学航天技术系!长沙;410073;国防科技大学航天技术系!长沙;410073

发布日期:2021-08-15

THE ANALYSIS OF INTERIOR BALLISTIC DISPERSION OF SRM DURING THRUST TERMINATION WITH MONTE CARLO METHOD

Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073;Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073;Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073;Dept. of Aerospace Technology, National Univ. of Defence Technology, Changsha, 410073

Published:2021-08-15

摘要/Abstract

摘要： 用辨识方法确定了带反喷固体火箭发动机推力终止过程中的瞬变参数，视这些参数是服从正态分布的随机变量，用Montecarlo方法分析了推力终止过程内弹道的散布。结果显示，推力终止过程中不同时刻压力散布服从正态分布，据此求出了弹道散布的数字特征和分布函数，研究结果对带反喷管的固体火箭发动机设计有参考价值。

关键词: 固体推进剂火箭发动机;内弹道计算;随机取样;计算机仿真;多数识别

Abstract: As the transient parameters during thrust termination of SRM with four reverse nozzles are determined by identification techniques and considered as random variables which obey normal distribution, the interior ballistic dispersion during thrust termination can be analyzed by Monte Carlo method. The reults show that the pressure dispersion obeys normal distribution. The digital characteristic parameters and distribution function are also determined in this paper. This study is useful for the design of SRM with reverse nozzle.

Key words: Solid propellant rocket motor;Interior ballistic calculation;Random scanning;Computerized simulation;Parameter identification

杨涛,郑荣跃,方丁酉,夏智勋. 用Monte Carlo法分析固体火箭发动机推力终止过程内弹道散布[J]. 推进技术, 1997, 18(6): 31-35.